Rocket booster stage landing apparatus

ABSTRACT

A rocket booster stage landing apparatus for more reliably landing a returning booster stage for reuse in propelling and launching subsequent main rockets.

FIELD OF THE INVENTION

This invention relates to the recovery of rocket booster first stage forreuse in subsequent rockets.

BACKGROUND OF THE INVENTION

Rockets for delivering large payloads into space require a booster stagepacked with fuel to lift the entire rocket to a desired altitude beforedisengaging from the main rocket with payload that continues on aspecified path. The booster stage then falls to earth and may beretrieved in the ocean as salvage. To reduce costs, rocket boosterstages are being designed to return to earth in a controlled manner tobe reused.

Reuse requires different procedures depending on the weight of the mainrocket. Rockets with booster stages follow a curved path into the upperatmosphere. When the booster stage is disconnected from the main rocket,recovery may occur at the original land lift of site or on a floatingplatform pulled by a ship at ocean. For smaller main rockets, enoughfuel remains in the booster stage after disconnection to reverse thefirst stage and direct it back to its launch site within an appropriatediameter target area. For larger main rockets, not enough fuel remains,and the returning rocket booster stage must be guided along the shortestpath to a platform over water with floating platform with an appropriatetarget pulled by a ship to a desired location for the returning stage.Care must be taken to have the returning booster stages land verticallyand remain vertical until stationary with no further emissions of hotgases from ignited fuel. Currently, SpaceX is estimating with theirFalcon 9 booster stages will make 70% of their landings on ground and30% of their landings on a floating platform at ocean.

There is a need for a rocket booster stage retrieval apparatus that isbased on the ground or on the floating platform that is configured tobetter guide the rocket booster stage into a safe vertical landing.

SUMMARY OF THE INVENTION

I have invented a rocket booster stage landing apparatus that isconfigured to improve safe retrieval of booster stages for reuse.Because the invention is a stand-alone apparatus, it does not add weightto the rocket by incorporating landing elements into the landing boosterstage.

Specifically, the rocket booster stage landing apparatus comprises fourelements, a platform, a dampening cushioning device, an exhaust diffuserdevice, and a truncated hollow cone. The platform comprises an area, aperimeter, a top, a bottom, and a center. The dampening cushioningdevice comprises a base attached to the of the platform, a dampeningregion above the bottom region of the base, and a protruding top with abase element attached to the dampening region and configured toparticipate in diffusing ignited fuel away from the dampening cushioningdevice and the landing site of the landing booster stage and avoidhaving the hot gas blowing back to the landing rocket booster stage. Theexhaust diffuser device comprises a base with a first diameter, a firstinside surface, and a first edge in communication with the platform toform multiple openings configured to direct hot gases from ignited fuelfrom the landing rocket booster stage away from the dampening cushioningdevice on the platform, the landing site of the landing booster stage,and avoid having the hot gas blowing back to the landing rocket boosterstage, a mid-region with a second inside surface and a second diameterattached to the dampening cushioning device and the second insidesurface, and an upper section with a third diameter, a third insidesurface, and a third edge configured to releasably attach to a base of alanding rocket booster stage, the exhaust diffuser device having, atruncated cone shape with an outer surface and the first diameter islarger than the second diameter that is larger than the third diameter.The truncated hollow cone comprises an outer surface, an inner surface,an upper end having an upper opening with a fourth edge with a fourthcircumference and an appropriate fourth diameter to permit access of thelanding rocket booster stage, a lower region with a fifth diameter lessthan the fourth diameter and configured to expose the third edge of theexhaust diffuser device and a flared bottom with a sixth diameter and aninside surface between the fifth diameter and the sixth diameter that isconfigured to enclose and be in communication with the outer surface ofthe exhaust diffuser device to direct ignited fuel to the diffuser topand outward away from the dampening cushioning device and avoid havingthe hot gas blowing back to the landing rocket booster stage.

A method of using a rocket booster stage landing apparatus to retrieve alanding booster stage sufficiently cleanly to reuse the landing boosterstage with minimal refurbishments comprises six steps. One step isproviding a rocket booster stage landing apparatus comprising fourelements that have been discussed above. Another step is positioning therocket booster stage landing apparatus over a pre-determined areaconsisting of either stationary land or a floating platform over waterthat is going to be used as a target. Still another step is providing alanding booster stage descending over a pre-determined target on earthafter decoupling from a main rocket. Another step is refining theposition of the rocket booster stage landing apparatus in relation tothe overhead descending rocket booster stage to receive the landingbooster stage. Still another step is retrieving the rocket booster stageintact to form a retrieved rocket booster stage.

My invention provides a way to transport larger payloads into space in amore economical manner. The apparatus provides a dampening cushioningdevice to dampen the shock of landing on a firm surface. It alsoprovides more massive and stable structure to maintain a more stablevertical orientation during landing. Further, it provides outlets torapidly remove and reduce destructive heating of rocket stage exhaustduring landing. My invention reduces weight on the rocket booster stageby removing the built-in landing system such as the four landing legs inthe current Falcon 9 booster stage. It also reduces the amount of fuelneeded for existing payloads or allows for larger payloads. In addition,not incorporating the landing system reduces rocket costs and allowingfor reuse of the booster stage reduces rocket costs. All of thesebenefits result in a greater chance of safe landing of a booster stageon land or on a floating platform on water that permits reuse of thebooster stage with less expensive refurbishing operations.

BRIEF DESCRIPTION OF THE DRAWINGS

The invention will become more fully understood by the accompanyingdrawings, wherein like elements are represented by like referencecharacters, which are given by way of illustration only and thus are notlimitative of the example embodiments herein.

FIG. 1 is a perspective exploded view of an embodiment of the inventionreceiving a landing booster stage with partially closed grasping armswith separated ends that support the landing booster stage

FIG. 2 is a perspective exploded view of an embodiment of the inventionreceiving a landing booster stage with partially closed connectedgrasping arms that encircle the landing booster stage.

FIG. 3 is a cross section showing a collapsed side view of theembodiment shown in FIG. 2 .

FIG. 4 is a perspective view with a cutout of the embodiment of FIG. 2showing just the exhaust diffuser device connected to the dampeningcushioning device and several exhaust deflection elements.

FIG. 5 is a larger view of a cross section of the lower part of theembodiment shown in FIG. 3 showing a dampening system and an extinctionsystem that comprises pressurized accumulator and extinguishing agentdelivery network.

FIG. 6 is a cross-section of the invention shown in FIG. 3 withdifferent angle showing the dampening cushioning device, andextinguishing spray nozzle with exhaust channels.

FIG. 7 is a perspective view of the bottom of the platform shown in FIG.6 but of a larger area with cut-away showing sets of wheels,accumulators, batteries, the dampening cushioning device, and severalangled exhaust deflector elements.

FIG. 8 is a cross-section of a perspective view of a dampeningcushioning device shown in FIG. 5 but with the device half collapsed bythe landing rocket booster stage.

FIG. 9 is a cross-section of the invention shown in FIG. 7 but with thelanding rocket booster stage landed.

While the invention is amenable to various modifications and alternativeforms, specifics thereof have been shown by way of example in thedrawings and will be described in detail below. It is to be understood,however, that the intention is not to limit the invention to theparticular embodiments described. On the contrary, the invention isintended to cover all modifications, equivalents, and alternativesfalling within the scope of the invention as defined by the appendedclaims.

DETAILED DESCRIPTION OF SOME EMBODIMENTS OF THE INVENTION

Many rocket booster stages are currently being deposited in the waterand retrieved for salvage. There is a growing effort to retrieve thebooster stages in a sufficiently undamaged state to be reused withminimal refurbishment operations to make space flight more economical.Some of these are platforms pulled by boats in the ocean that permit thebooster stages to have a larger percentage of the fuel devoted tolifting larger payloads because less fuel is needed to just drop to theearth wherever they are and have a floating platform to be towed by aboat to be where the booster stage is landing. However, maintaining avertical landing can be challenging as the ocean moves, the wind blowson side on the booster stage or both.

Some booster stages are being designed to land on an area that providesa hard stable surface. The landing site is generally either the takeoffsite or a preselected land site. However, more fuel is required, anddifferent challenges occur in maintaining a vertical orientation duringlanding. A higher percent of fuel is needed to land a booster on land,at a particular spot, such as, for example, liftoff, because fuel mustbe expended to guide the booster stage back to where lift off occurredor to another preselected site.

In both cases, additional concerns exist. One concern is the boosterstage must be landed in a stable fashion to prevent it from tipping overand exploding. Another concern is the burning fuel exhaust must besafely dissipated away from the landing stage to prevent damage. Stillanother concern is cushioning the landing to minimize damage to thebooster stage. Anything added to the booster stage to address theseconcerns adds weight that decreases the percent of the fuel that can beused to move the main rocket to its destination.

The invention addresses the challenges by providing a rocket boosterstage landing apparatus separate from the booster stage. The apparatusallows for a focus on aspects needed to minimize booster stage damageduring landing without increasing the percent of fuel required. Someelements may be quite heavy but minimize these problems and focus onmaintaining safe booster stage landing for subsequent reuse. Inaddition, the apparatus of the invention is reusable with minimalrefurbishing operations.

Specifically, the rocket booster stage landing apparatus comprises fourelements, a platform, a dampening cushioning device, an exhaustdiffusion device, and a truncated hollow cone.

The platform comprises an area, a perimeter, a top, a bottom, and acenter. The area is large enough to offer a stable site for the rocketbooster stage landing apparatus. A larger area may be beneficial whenfloating the apparatus than when positioning it on land.

In some embodiments, the platform comprises multiple channels to allowhot gases from ignited fuel from the landing booster stage to bedisplaced away from the booster stage.

In some embodiments, the platform comprises accumulators containingextinguishing agent used to cool the landing booster stage.

In some embodiments, the platform further comprises wheels configured tomove the rocket booster stage landing apparatus within an area to beself-positioning to a descending overhead target of a ground platform oron a floating platform. The wheels are configured to better align theapparatus with the actual location where the landing booster stage istargeting. In some embodiments, the wheels are motor-driven andmotor-positioned. The wheels may be similar to those on large aircraft.The wheels may be in pairs. In some embodiments, the wheels aredirectional. The wheels may be individually driven in both speed anddirection of rotation to allow for more precise movement to a targetarea. In some embodiments the wheels are automatically or manuallyactuated and remotely driven and positioned using sensors or visuallythrough a webcam to position the apparatus under the final position inspace of the descending booster stage.

The dampening cushioning device is used to further decrease the speed ofthe landing booster to a stationary position stage to permit safelanding and minimize reconditioning before reuse of the booster stage.The dampening cushioning device comprises a base attached to the centerof the platform, a dampening region above the bottom region of the base,and a protruding top with a base element attached to the dampeningregion and configured to participate in diffusing hot gases from ignitedfuel away from the dampening cushioning device and the landing site ofthe landing booster stage and avoid having the hot gas blowing back tothe landing booster stage.

In one embodiment, the base of the dampening cushioning device isattached to the platform, usually at its center to maximize horizontalstability of the rocket booster stage landing apparatus during use. Thedampening region comprises a shell, a piston, and a dampening element.The shell attaches to the base and that encompasses the dampeningelements and a horizontal piston element that rests on top of thedampening element. The piston further comprises upper vertical pistonelements that extend from the top of the horizontal piston element andpass moveably through the top of the shell to attach to the base elementof the protruding top. The piston also comprises a lower verticalelement that extends from the bottom of the horizontal element, throughthe base of the shell attached to platform and moveably through theshell into the platform below the base. When weight is applied to theexhaust diffuser device, the upper and lower vertical piston elementspass through the shell pushing the horizontal piston element downagainst the dampening element to compress it against the bottom of theshell. The dampening element for the above dampening cushioning deviseis a large area actuator. Other dampening cushioning devises may be usedwith other dampening elements such as the heavy metal springs andmagnetic repelling systems but require dampening cushioning devices withdifferent structure. The protruding top region has multiple nozzlesconfigured to spray pressurized extinguishing agent into the bottom ofthe landing stage to extinguish any remaining ignited fuel and to removethe heat.

In another embodiment, the bottom of the upper region is incommunication with to the upper end of a lower stabilizing truncatedcone whose bottom end is affixed to the platform, and the base elementof the protruding top is attached to the upper end of an upperstabilizing truncated cone whose bottom end is affixed to the base ofthe exhausting diffuser device for additional stability of the dampeningcushioning device during landing.

The exhaust diffuser device comprises a base with a first diameter, afirst inside surface, and a first edge in communication with theplatform to form multiple openings configured to direct ignited fuelfrom the landing rocket booster stage away from the dampening cushioningdevice on the platform and the landing site of the landing booster stageand avoid having the hot gas blowing back to the landing rocket boosterstage, a mid-region with a second inside surface and a second diameterattached to the dampening cushioning device and the second insidesurface, and an upper section with a third diameter, a third insidesurface, and a third edge configured to releasably attach to a base of alanding rocket booster stage, the exhaust diffuser device having, atruncated cone shape with an outer surface and the first diameter islarger than the second diameter that is larger than the third diameter.This is not easily accomplished with a landing booster stage that reliesupon itself to provide all elements of achieving a stable verticallanding requiring minimal refurbishing operations before reuse insubsequent rocket launches.

The mid-region comprises attached to the base of the upper region of thedampening cushioning device multiple exhaust deflectors passing from thesecond inside surface of the exhaust diffuser device to bottom area ofthe protruding top region of the dampening cushioning device. Eachdeflector is angled down on both sides to direct exhaust down andoutward to through multiple openings at the bottom of the exhaustdiffuser device where it contacts the platform to exit channels on theplatform. This region is where the landing booster stage bottom contactsthe rocket booster stage landing apparatus.

The top opening with a third diameter is large enough to accommodate alanding booster stage.

In some embodiments, extinguishing agent is passed to the base of thelanding booster stage to extinguish any remaining ignited fuel and tocool it off. Extinguishing agent, stored in accumulators. It isconfigured to pass from storage tanks or accumulators dispersed aboutthe platform through flexible hoses to the base of the dampeningcushioning device and up through the nozzles in the protruding toptoward the landed booster stage bottom. Exhaust agent, now in the formof hot gases, is passed along the path of the leaving exhaust.

The extinguishing agent comprises materials that are stable andfunctional as extinguishing agents at temperatures experienced duringexposure of burning rocket fuel and added to temperatures caused byfriction with the atmosphere during booster stage landing. Suitableexhausting agents include, for example, at least one of liquid carbondioxide or pressurized powder extinguishing agents that are storedtypically under pressures of over 1000 psi.

The truncated hollow cone comprises an outer surface, an inner surface,an upper region, a lower region, and a flared bottom region. The upperregion has an upper end having an upper opening with a fourth edge witha fourth circumference and an appropriate fourth diameter to permit easyaccess of the landing rocket booster stage. The lower region with afifth diameter less than the fourth diameter and configured to exposethe third edge of the exhaust diffuser device. This slope allows alanding booster stage that is slightly off course to be directed to thecenter of the platform. The truncated hollow cone also comprises aflared bottom region with a sixth diameter and an inside surface betweenthe fifth diameter and the sixth diameter that is configured to encloseand be in communication with the outer surface of the exhaust diffuserdevice to direct hot gases from the ignited fuel to the diffuser top andoutward away from the dampening cushioning device and the landing siteof the landing booster stage and avoid having the hot gas blowing backto the landing rocket booster stage.

The truncated hollow cone is mounted on the platform and vertically tothe dampening cushioning device on the platform. The first diameter isthe diameter of a target area that the booster stage is configured toland within. The lower diameter is just larger than the diameter of thelanding booster stage. The height, preferably above the center ofgravity of the booster stage to minimize occurrence of toppling over ofthe booster stage. The height is below the full height of the boosterstage to minimize weight that provides minimal further stability.

Appropriate dimensions depend upon the actual rocket booster stage thatis being landed. A Falcon 9 rocket by SpaceX will be used in thisdocument but the invention will benefit in a comparable manner otherrockets with booster stages that are desired to be retrieved safely. TheFalcon 9 is typically 63.3 meters (m) (207.8 feet (ft)) high, 3.7 m (12ft) in diameter, and 549,000 kg (1,208,000 labs). Its nine first-stageMerlin engines generate 1.3 million pounds of thrust at sea level,rising to 1.5 million pounds of thrust as Falcon 9 climbs out of theEarth's atmosphere. The core itself of the first stage, called thebooster stage that is being retrieved, is about 47.7 m (156.5 ft) high,and 3.7 m (12.0 ft) in diameter. The four landing legs, together, areabout 23,000 kg (50,610 lbs). The rocket has a height of between justover half that of the booster stage and under the full height of thebooster stage. Its nine engines Merlin 1D help it lift payloads intospace and land the core safely on the ground. Together with a secondstage, it is known as the Falcon 9 version 1.

For the above booster stage, an embodiment of the truncated hollow conehas a first diameter of approximately 8.5 m (28 ft). The landing boosterstage passes from a speed of 20 mph or 29 fps at an altitude of 2000 ftto stationary on landing.

For some embodiments, the truncated hollow cone further comprises acollection of multiple arms with a first arm end rotatably attachedequally distanced about the first circumference of the first end, asecond arm end extending upward and outward from the first end, havingcurved horizontal tips, and configured to rotate inward to encompass alanding rocket booster stage without the adjacent tips touching eachother.

For some embodiments, the truncated hollow cone of the previousembodiment further comprises a collection of multiple rod elements eachextending horizontally from each second end to form a circularcollection of rods about the landing booster stage with adjacent rodstouching and tangling and configured to better stabilize the verticalorientation of the landing rocket booster stage. This embodiment offersincreased vertical stability of the landed booster stage than theversion where the adjacent second end do not touch.

In some embodiments, the truncated hollow cone further comprising atleast one powered winding contacting the inner surface of the cone in anappropriate configuration configured to create a magnetic field withinthe cone capable of slowing down a descending booster stage. Magneticfields place a drag upon the landing booster stage that increases withelectrical power provided to the windings forming the magnetic fields.The magnetic field is only on for a few seconds as the landing boosterstage passes through the magnetic field. This further increases theefforts of the dampening provided by the cushioning device mentionedabove in the platform.

Materials used for the rocket booster stage landing apparatus vary asneeded. In general, materials in contact with the landing booster stageshould be strong enough to remain functional under the weight andtemperatures involved during use. Those not in the presence ofsignificant magnetic fields may use magnetically attracted materialssuch as, for example, carbon steel. Embodiments in the presence ofstrong magnetic fields may use non-magnetic materials such as, forexample, stainless steel, titanium, and non-magnetic alloys of titanium.Use of materials with structures having composite materials such asfiber glass, fiber carbon, and a honeycomb construction offerssignificant reductions in weight without corresponding loses instrength.

FIGS. 1-9 further illustrate the nature of several embodiments of theinvention. Similar elements have the same numbers.

FIG. 1 is a perspective exploded view of an embodiment of the inventionreceiving a landing booster stage with partially closed grasping armswith separated ends that support the landing booster stage. A landingbooster stage (A) is shown with its bottom end region (B) entering anembodiment of the rocket booster stage landing apparatus (100)comprising a platform (120) with a center 122 and multiple exhaustchannel, a dampening cushioning device 130 attached to platform 120 andan exhaust diffuser device (150) configured to be in communication withthe platform 120 at the bottom edge (152) of exhaust diffuser device 150with cutouts (154) forming tops of exhaust outlets. The truncated hollowcone (170) is shown with a bottom edge (172) narrowing in a lowersection (174) before widening to a top edge (176). A magnetic fieldgenerator (178) is at the top of truncated hollow cone 170. The flaredbottom (180) is configured to encompass in close contact an outersurface (158) of exhaust diffuser device 150. A collection of multiplearms (190) is rotatably attached to the upper part of truncated hollowcone 170. Arms 190 with small horizontal ends (192) are shown nearlyclosed around landing booster stage A.

FIG. 2 is a perspective exploded view of an embodiment of the outerinvention receiving a landing booster stage with partially openconnected grasping arms that encircle the landing booster stage. Thisembodiment is similar to that shown in FIG. 1 except small ends 192 arelong rods (194) that are connected to each other when the arms are fullyencircled around edge 176 booster stage bottom 176 of landed boosterstage A.

FIG. 3 is a collapsed side view of the embodiment shown in FIG. 2 withbooster stage A landed. Booster stage end C of bottom B is shown restingon top end 156 of exhaust diffusing device 150. The base element (136)of protruding top (134) of dampening cushioning device 130 is attachedto multiple angled deflector elements 160 (also shown in FIG. 4 and FIG.6 ) of exhaust diffuser device 150 and had multiple holes (166) fromwhich pressurized extinguishing agent is sprayed into the chamber formedby the inside surface (168) of exhaust diffuser 150 and the upperstabilizing truncated cone (146) attached to the dampening cushioningdevice at 146 a (shown in FIG. 5 ) and the exhaust diffuser 150 (shownin FIG. 5 ) at 146 b. Exhaust agent is moved from pressurized tanks orcontainers (140) toward inside of upper region 134 through holes 166.Then exhaust gases exit through channels (144) to openings (149)(together shown in FIG. 6 ) to openings (125) to channels 128 inplatform (120) (together shown in FIG. 6 ).

FIG. 4 is a perspective view with a cutout of the embodiment of FIG. 2showing just the exhaust diffuser device connected to the dampeningcushioning device and several angled exhaust deflection elements.Exhausting diffuser device 150 is shown cut away to show multiple angleddeflector elements 160 attached to inside surface (168) of exhaustdiffuser device 150 and to protruding top 134 of dampening cushioningdevice 130.

FIG. 5 is a larger view of a cross section of the lower part of theembodiment shown in FIG. 3 showing a dampening system and anextinguishing system that comprises pressurized accumulator andextinguishing agent delivery network. Base element 136 of protruding top134, circular element (163) of the mid-section of the exhaust diffuser150, and horizontal piston element (138) are shown with top of dampeningchamber (139) within shell (142) and upper region encompassing verticalpiston elements (137). With upper ends (135). Stabilizing truncated cone146 is attached to dampening cushioning device 130 at (146 a) andexhaust diffuser device 150 at (146 b). Lower stabilizing truncated cone(148) is in communication with dampening cushioning device 130 at (148a) and attached to platform 120 at (148 b). Pressurized extinguishingagent accumulators 140 is shown with extinguishing agent configured topass up through hoses (162) and then dampening cushioning device toprotruding top 134 and through spray nozzles 166 into the underside ofupper region of exhausting diffuser. Extinguished formerly ignited fuelthen passes over multiple angled deflector elements 160.

FIG. 6 is a cross-section of the invention shown in FIG. 3 withdifferent angle showing the dampening cushioning device, andextinguishing spray nozzle 166 with exhaust channels 144. Theextinguished formerly ignited fuel passes through opening 149 in theexhaust diffusing device 150 to openings 125 in the platform 120 tochannels 128 in platform 120

FIG. 7 is a perspective view of the bottom of the platform shown in FIG.3 but of a larger area with cut-away showing sets of wheels,accumulator, batteries, inside of the dampening cushioning device, andseveral angled exhaustion deflector elements. Platform 120 is shown withexhaust diffuser device 150 over platform center 122 with edge 152contacting platform and cutouts 154 over platform channels (128)configured to direct extinguished formerly ignited fuel away frombooster stage A. Multiple angled deflector elements 160 as visible.Pairs of wheels (124) are shown each with their battery pack (126). Alsoshown are pressurized extinguishing agent accumulators 140 placed inplatform 120.

A first method of using a rocket booster stage landing apparatus toretrieve a landing booster stage sufficiently cleanly to reuse thelanding booster stage with minimal refurbishments comprises six steps.One step is providing a rocket booster stage landing apparatuscomprising four elements that have been discussed above. Another step ispositioning the rocket booster stage landing apparatus over apre-determined area consisting of either stationary land or a floatingplatform over water that is going to be used as a target. Still anotherstep is providing a landing booster stage descending to a pre-determinedtarget area on earth containing the rocket booster stage landingapparatus after decoupling from a main rocket. Another step is refiningthe position of the rocket booster stage landing apparatus to becentered to the descending landing booster stage to receive the landingbooster stage Refinement may be accomplished automatically or manuallyand by using sensors or visual means through a webcam. Still anotherstep is retrieving the rocket booster stage intact to form a retrievedrocket booster stage. In some embodiments of the first method, themethod of using a rocket booster stage landing apparatus comprisesanother step. The fifth step is reusing the retrieved rocket boosterstage with minimal refurbishing operations.

In some embodiments of the first method, the method of using a rocketbooster stage landing apparatus comprises another step. The fifth stepis reusing the retrieved rocket booster stage with minimal refurbishingoperations.

In some embodiments of the first method, the method uses an additionalelement in the booster stage landing apparatus and an additional step.The additional element is a collection of multiple arms with a first armend rotatably attached equally distanced about the first circumferenceof the first end of the truncated hollow cone a second arm end extendingupward and outward from the first end. Each second end may or may nothave curved horizontal tips and is configured to rotate inward toencompass a landing rocket booster stage without the adjacent tipstouching each other. The additional step is drawing the collection ofmultiple arms inward around the landing booster stage as it descendsonto the rocket booster stage landing apparatus

In some embodiments of the previous method, the method uses anadditional element in the booster stage landing apparatus and anadditional step. The additional element is collection of a multiple rodelements each extending horizontally from each second end to form acircular collection of rods about the landing booster stage withadjacent rods touching and configures to stabilize the verticalorientation of the landing rocket booster stag. The indrawn rods form acircular pattern having a diameter similar to the landed rocket boosterstage to increase the ease of the returned booster stage remainingvertical and not falling over to become damaged. The additional step isdrawing the collection of multiple rods inward, as the collection ofarms are drawn inward, around the landing booster stage as it descendsonto the rocket booster stage landing apparatus. This providesadditional support for holding the booster stage stable than just usingthe arms alone as provided in the previous embodiment.

In some embodiments of the first method, the truncated hollow conefurther comprises at least one powered winding contacting the innersurface of the cone in an appropriate configuration configured to createa magnetic field within the cone capable of slowing down a descendingbooster stage to reduce its descending speed still further without usingmore fuel.

In some embodiments of the first method, the platform further comprisesmultiple spray nozzles configured to deposit extinguishing agent ontothe dampening cushioning device and base of a booster stage to thedampening cushioning device to reduce heat stress upon the landingapparatus and base of the landing booster stage.

In some embodiments of the first method, the platform further compriseswheels configured to move the rocket booster stage landing apparatus tobe self-positioned to a descending overhead target area of ground or ona floating platform.

In some embodiments of the previous method, the wheels are from a groupconsisting of motor driven, directional, and manually remote driven.

FIGS. 8 and 9 further illustrate the interaction of the various partsduring landing.

FIG. 8 is a cross-section of a perspective view of a dampeningcushioning device shown in FIG. 5 but with the device half collapsedwithin its shell 142 by the landing rocket booster stage pushing onexhaust diffuser top (not shown) which causes mid-section 160 (notshown) attached base element 136 of protruding top 134 that is attachedto the tops 135 of upper vertical piston elements 137. As verticalpiston elements are pressed down, the horizontal piston element 138pressed down on the top of the dampening elements 139 within dampeningcushioning device shell 142 and pressed the lower vertical pistonelement into a cavity in the platform below base 132. In this view, thedistance between horizontal piston element 138 of upper region andbottom region 132 of shell 142 is less as weight of landing boosterstage is increasingly depresses the dampening elements 139.

FIG. 9 is a cross-section of the invention shown in FIG. 7 but with thelanding booster stage landed. Note the minimal height of the dampeningelements 139 and the extension of the lower vertical piston elementbelow the base.

Other modifications and changes regarding my invention will be apparentto those skilled in the art. The invention is not limited to theembodiments chosen for purposes of disclosure and covers all changes andmodifications that do not constitute departures from the true spirit andscope of this invention.

I claim:
 1. A rocket booster stage landing apparatus for receiving a landing booster stage with a landing booster stage base on a landing site comprising a platform comprising an area, a perimeter, a top, a bottom, and a center, a dampening cushioning device comprises a base attached to the center of the platform, a dampening region above the base, and a protruding top with a base element attached to the dampening region and configured to participate in diffusing hot gas from ignited fuel away from the dampening cushioning device and the landing site of the landing booster stage and avoid having the hot gas blowing back to the landing rocket booster stage, an exhaust diffuser device comprising a base with a first diameter in communication with the platform to form multiple openings configured to direct hot gas from ignited fuel from the landing rocket booster stage away from the dampening cushioning device on the platform, a mid-region with a second inside surface and a second diameter attached to the dampening cushioning device and the second inside surface, and an upper section with a third diameter, a third inside surface, and a third edge configured to releasably attach to a base of a landing rocket booster stage, the exhaust diffuser device having, a truncated cone shape with an outer surface and the first diameter is larger than the second diameter that is larger than the third diameter; and a truncated hollow cone comprising an outer surface, an inner surface, an upper end having an upper opening with a fourth edge with a fourth circumference and an appropriate fourth diameter to permit access of the landing rocket booster stage, a lower region with a fifth diameter less than the fourth diameter and configured to expose the third edge of the exhaust diffuser device and a flared bottom with a sixth diameter and an inside surface between the fifth diameter and the sixth diameter that is configured to enclose and be in communication with the outer surface of the exhaust diffuser device to direct ignited fuel to the diffuser top and outward away from the dampening cushioning device and from the landing site of the landing booster stage to avoid blow back and damage to the landing booster stage.
 2. The rocket booster stage landing apparatus of claim 1, wherein the truncated cone further comprises a collection of multiple arms with a first arm end rotatably attached equally distanced about the first circumference of the first end, a second arm end extending upward and outward from the first end, having curved horizontal tips, and configured to rotate inward to encompass a landing rocket booster stage without the adjacent tips touching each other.
 3. The rocket booster stage landing apparatus of claim 2, wherein the truncated cone further comprises a collection of multiple rod elements each extending horizontally from each second end to form a circular collection of rods about the landing booster stage with adjacent rods touching and tangling and configures to stabilize the vertical orientation of the landing rocket booster stage.
 4. The rocket booster stage landing apparatus of claim 1, wherein the truncated cone further comprising at least one powered magnetic field generator about the upper end of the truncated cone configured to slow down a landing rocket booster stage.
 5. The rocket booster stage landing apparatus of claim 1, wherein the protruding top of the dampening cushioning device further comprises multiple nozzles configured to direct extinguishing agent toward and cool the landing booster stage.
 6. The rocket booster stage landing apparatus of claim 5, wherein the extinguishing agent comprises at least one of liquid carbon dioxide or a pressurized powder extinguishing agent.
 7. The rocket booster stage landing apparatus of claim 1, wherein the platform further comprises wheels configured to move the rocket booster stage landing apparatus to be properly positioned to receive a landing booster stage on land or on a floating platform.
 8. The rocket booster stage landing apparatus of claim 7, wherein the wheels are motor driven.
 9. The rocket booster stage landing apparatus of claim 7, wherein the wheels are directional.
 10. The rocket booster stage landing apparatus of claim 7, wherein the wheels are manually activated and remotely driven.
 11. A method of using a rocket booster stage landing apparatus for receiving a landing booster with a base comprising providing a rocket booster stage landing apparatus comprising a platform comprising an area, a perimeter, a top, a bottom, and a center; a dampening cushioning device comprises a base attached to the hollow center of the platform, a dampening region above the base, and a protruding top with a base element attached to the dampening region and configured to participate in diffusing hot gas from the ignited fuel away from the dampening cushioning device and the landing site of the landing booster stage and avoid having the hot gas blowing back to the landing rocket booster stage; an exhaust diffuser device comprising a base with a first diameter in communication with the platform to form multiple openings configured to direct hot gas from the ignited fuel from the landing rocket booster stage away from the dampening cushioning device on the platform and the landing booster stage, a mid-region with a second inside surface and a second diameter attached to the dampening cushioning device and the second inside surface, and an upper section with a third diameter, a third inside surface, and a third edge configured to releasably attach to a base of a landing rocket booster stage, the exhaust diffuser device having, a truncated cone shape with an outer surface and the first diameter is larger than the second diameter that is larger than the third diameter; and a truncated hollow cone comprising an outer surface, an inner surface, an upper end having an upper opening with a fourth edge with a fourth circumference and an appropriate fourth diameter to permit access of the landing rocket booster stage, a lower region with a fifth diameter less than the fourth diameter and configured to expose the third edge of the exhaust diffuser device and a flared bottom with a sixth diameter and an inside surface between the fifth diameter and the sixth diameter that is configured to enclose and be in communication with the outer surface of the exhaust diffuser device to direct hot gas from ignited fuel to the diffuser top and outward away from the dampening cushioning device and from the landing site of the landing booster stage to avoid blowing back and damaging the landing booster stage; positioning the rocket booster stage landing apparatus over a pre-determined area consisting of either stationary land or a floating platform over water that is going to be used as a target; providing a landing booster stage descending to a pre-determined target area on earth containing the rocket booster stage landing apparatus after decoupling from a main rocket; refining the position of the rocket booster stage landing apparatus to be centered to the descending landing booster stage to receive the landing booster stage; and retrieving the rocket booster stage intact to form a retrieved rocket booster stage.
 12. The method of using a rocket booster stage landing apparatus of claim 11 further comprising the step of reusing the retrieved rocket booster stage with minimal refurbishing operations.
 13. The method of using a rocket booster stage landing apparatus of claim 11, wherein the truncated cone further comprises a collection of multiple arms with a first arm end rotatably attached equally distanced about the first circumference of the first end, a second arm end extending upward and outward from the first end, having curved horizontal tips, and configured to rotate inward to encompass a landing rocket booster stage without the adjacent tips touching each other and a collection of multiple rod elements each extending horizontally from each second end to form a circular collection of rods about the landing booster stage with adjacent rods touching and tangling and configures to stabilize the vertical orientation of the landing rocket booster stage, and the method further comprises the step of drawing the collection of multiple arm and rods inward around the landing booster stage as it descends onto the rocket booster stage landing apparatus.
 14. The method of using a rocket booster stage landing apparatus of claim 11, wherein the truncated cone further comprises at least one powered magnetic field generator about the upper end of the truncated cone configured to slow down a landing booster stage to reduce its descending speed still further without using more fuel.
 15. The method of using a rocket booster stage landing apparatus of claim 11, wherein the upper region of the dampening cushioning device further comprises multiple openings configured to direct extinguishing agent toward the landing booster stage to extinguish the remaining ignited fuel and to cool it.
 16. The method of using a rocket booster stage landing apparatus of claim 11, wherein the platform further comprises wheels configured to move the rocket booster stage landing apparatus to where a descending overhead booster stage is landing on ground or on a floating platform.
 17. The method of using a rocket booster stage landing apparatus of claim 16, wherein the wheels are from a group consisting of motor driven, directional, and manually remote driven. 